Experimental Investigation of Supersonic Flows with Separated Regions in Ducts

摘要

As applied to supersonic diffusers of different purpose and scramjet enginesseparation flows in various geometry ducts are investigated. Flow Mach and Reynolds numbers at the entrance to the ducts ranged from I to 6 and from 4.IO% to 7.1O%, respectively. The transition from supersonic flow to subsonic flow efficiency defined by the transition region length and pressure recovery.